Planoorapji co



Z Qk-QB SR 1. F. WEBB, SR.

AEROPLANE. lCATlON FILED NOV. 14. 1917. 1 309 710 Patented July 15,

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TORNEYS INVENTOR J 5/ BY Tms coLunmA PLANDGRAPH co.. WASHINGTON, D. c.

244. AERONAUHC? F. WEBB, SR.

AEROPLANE. APPLICATlON FILED NOV. 14. I917- 1 309,710, Patented July 15,1919.

, TSHEETS-SHEET 2- l l I I I l THE COLUMBIA ILANDGRAPH cm, WASHINGTON.n. c.

J. F WEBB, SR.

AEROPLANE.

APPLICATION FILED NOV. 4, 1917. 1,309,710. Patented July 15, 1919.

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INVENTOR Jean]? W565,J7:

THE COLUMBIA FLANDURAPH co., WASHINGTON. D- c.

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1. F. .WEBB, Sn.

' AEROPLANE.

APPLICATION FILED NOV. 14, 1911.

Patented July 15, 191% 7 SHEETS-SHEET 4 Tm: COLUMBIA Pum'oonnml co,WASHINGTON, n. C.

244. AERONAUTICS J; F. WEBB, Sn.

AEROPLANE.

MTLICATION FILED NOV. 14, IQI I. Patented 15 7 SHEETS-SHEET 5.

INVENTOR Tm: COLUMBIA PLANOGRAPH co., WASHINGTON. n. c.

r 244. AERONAUTICSVW i J. F. WEBB, Sn.

AEROPLANE.

APPLICATION FILED NOV. 14, 9|!- 1 ,309, 7 1 O, Patented July 15, 1919.

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' d iTTTORNEYs m: COLUMBIA PLANOQRAPM cm. WASHINGTON, n. c.

244. AEROVNAUTICSW J. F. WEBB, Sn.

AEROPLANE.

APPLICATION FILED- NOV. 14. I917- Patented July 15, 1919.

7 SHEETS-SHEET 7 INVENTOR fanmb, J7.

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24-4. AERONAU'TlUS UNITED STATES PATENT OFFICE.

JEAN F. WEBB, SR., OF NEW YORK, N. Y.

AEROPLANE.

1 309 71() Specification of Letters Patent. Patented July 15, 1919,

Application filed. November 14, 1917. Serial No. 201,979.

To all whom it may concern: chine, the auxiliary propellers being all Beit known that I, JEAN F. WEBB, Sn, intergeared and geared with the powerplant residing at New York, in the county of or power plants, wherebyshould a pro- New '1 ork and State of New York, have peller break, theload will be automatically 5 invented certain new and usefulImprovedistributed tothe remainder.

ments in Aeroplanes, of which the follow- The invention also resides inthose novel ing is a specification, details of construction, combinationand ar- The invention primarily has for its obrangement of parts, all ofwhich will be ject to provide a practical, powerful aerofirst fullydescribed, then be specifically 10 plane adapted for very heavy duty incompointed out in the appended claims and mercial use, such as carryingfast mail, exllustrated in the accompanying drawings, press, passengersor freight, and to that 111 which end the invention provides a structurepos- Flgure 1 is a perspective view illustrating sessing such unusuallifting and sustaining a machine embodying the invention in flight.

15 power that it will support and carry a F 1g. 2 is a top plan View ofthe machine much greater weight per given area, or shown in Fig. 1.number of square feet of plane surface, Fig. 3 is a front elevation ofthe same. than is possible by those aeroplanes now Fig. 4: is ahorizontal section of a porin use. tion of the machine shown in Fig. 2,taken 20 Another object of the invention is to Jlust below the upperplane, parts of the provide a structure having great flexibilitymidplane being broken away to show the of control while in flight, inrising and structure beneath. landing, and one having such stability andFlg. 5 is an enlarged end elevation of a steadiness of flight as torender the machine part of the machine shown in Fig. 1.

25 quite safe against unusual air disturbances. Fig. 6 is a detailsection showing one of Again, the invention has for its object theauxiliary propeller shaft bearings. to provide a multiplane structure(triplane Fig. 7 is a detail section showing the or more) one of theintermediate plane-sets flanged pinion in engagement with the rack ofwhich may be inclined to change the that shifts the midplane on itsaxis.

30 angle of incidence at will, and thereby aid Fig. 8 is a top plan Viewshowing the in effecting a rapid climb or descent and Invention asapplied to an aeroplane hava safer landing than can otherwise be ating aplurality of power plants, tai d, Fig. 9 is a front elevation of thestructure Another object of the invention is to Shown in Fig. 8.

35 combine, with such tilting planes, auxiliary Fig. 10 is a detail Viewof a portion of propeller units which are tiltable with the theinvention. said planes and are designed to add th ir In the drawings, inwhich like letters and efforts to increase the lifting and carryingnumerals of reference indicate like parts power of the machine as wellas the climbin all of the figures, 1 represents the fuseing power anddescent thereof, and also lage mounted in the usual way to be susto aidin preventing accidents in alighting, tained by the upper and lowerfixed planes as the angle of the auxiliary propellers 22 that are spacedapart by vertical and the tiltable planes can be changed in struts 3 anddiagonal braces 4, the braces such manner that the speed can be grad- 4serving to sustain the trunnion bearings 32 45 uated to a slow and safelanding without for the tiltable midplanes 6, the parts 1 to jar orshock. 4 being made as in the present practice,

A .further object of the invention is to and, per 86, constituting nopart of my inprovide for the joint or individual control vention. of thetiltable planes and the correspond- In applying my invention toaeroplanes,

50 ing pivotal movement of the auxiliary proone of the intermediateplanes 6 (the midpeller units at the two sides of the machine, plane ofthe present case) is provided with whereby they may be moved as one ormoved separately, as desired, to aid in controlling the stability andflight of the maa suitable light rectangular framework 7 which sustainsthe usual plane surface and to which framework the trunnions 5 aresecured, the frame 7 also being fastened to the shaft housing 8 of theauxiliary propelling mechanism by suitable securing clamps 9. 1Odesignates arcuate racks which are secured to the end bearings 11 of theauxiliary propelling mechanism housing 8 and which extend between thesupports 12 in which the trunnions 13 are journaled, the supports 12being suitably braced and secured to the plane structure.

The bearings 11 are provided with combination annular and thrust ballbearings 14; and serve to journal the auxiliary propeller shafts 15 onwhich the auxiliary propellers 16 are mounted. 17 indicates the gearboxes whose trunnions 13 are mounted in the supports 12, the gear boxesforming a continuation of the shaft housing 8 and inclosing beveledgears 1818, by means of Which the auxiliary propellers are driven fromthe countershaft 19 which is itself geared as at 20-20 with the drivingshaft 21 of the engine 22 that constitutes the main power plant of themachine. 23 indicates the main propeller which is driven from the engine22 in the usual manner, the construction of the engine 22 and thepropeller 23 being of the conventional type.

Each arcuate rack 10 (there being one provided for each auxiliarypropeller and tilting unit) has its front edge beveled as at 24 toreduce the wind resistance and the rack 10 is operated by a flangedpinion 25 on a shaft 26 which carries a worm gear 27 that meshes withthe worm 28 on the controlling shaft 29, there being preferably a shaft29 provided for the shaft 19 at each side of the machine so that theauxiliary controlling units and tilting planes at the two sides of themachine may be manipu lated either simultaneously as one orindividually, as may be found desirable in practice.

3O designates a support which carries bearings 31 for the shaft 26. 32designates the bearings supported by the diagonal braces 4 at the endsof the machine in which the trunnions 5, that sustain the tiltable plane6, are journaled. The diagonal braces 4 adjacent to the fuselage,support a bearing 34 in which is journaled the projecting portion 35 ofthe trunnion 36, through which passes the shaft 19; it being understoodthat the pivotal axes of the planes 6 are in transverse alinement andcoincident with the axis of the trunnions 13 on which the auxiliarypropeller units are carried.

The invention may be applied to aeroplanes having but a single powerplant, as shown in Figs. 14, inclusive, of the drawings, or it may beapplied to a structure embodying a plurality of power plant units andsuch a structure is shown in Fig. 8, from which it will he observed thata plurality of fuselages 11 are employed, each sustaining an engine orpower plant 22 to drive the main propellers 23 of which there are threeshown in the illustrations. When the invention is applied to such astructure, however, the various power plants are intergeared as at 37,so that the three main power plant units will operate as one, wherebyshould one of the engines break, the other engines will take care of theload and the shafts 19 are gear-connected at 2020 with the adjacentpower plant so that the auxiliary propellers and the niain propellerswill turn in unison, and in the event of one or the other of suchengines breaking, the load will be distributed between the remainder.

38 designates the usual horizontal rudder and 39 the usual verticalrudders of the aeroplanes, it being understood that the construction ofthe fuselage and the rudders of the machine may be in accordance withthe established practice, and the usual controls for effecting theoperation of the various parts may be provided, but as such, per 86,constitute no part of the present invention I have not deemed itnecessary to illns trate th same.

lVhile the invention has been described especially with reference toaeroplanes, it will be understood that it may be also adapted for use inhydroaeroplanes, in which event the hydroaeroplane floats will besubstituted in lieu of the alighting gear 40 shown, but as suchstructure of alighting gear and hydroplaning elements may be of theconventional type, further description and illustration of the same isthought to be unnnecessary.

In operation, the invention is especially advantageous in obtainingquick rising or dipping effects, according as the midplanes are tiltedupwardly or downwardly, with relation to the direction of flight, and itis also of great advantage in landing as by throwing the tilting planeupwardly as the machine nears the ground, the flight may be checked, andat the same time by thus increasing the angle of the tilting plane withrelation to the line of flight, a greater lifting effect is obtained atthe moment of landing, so as to engage the ground with less force andless danger of nosing the machine into the ground than would be the casewere all the planes stationary, and inasmuch as the auxiliary propellingmechanism turns with the tilting planes their effective action will beadded to that of. the tilting planes and thus the stability of themachine is greatly increased.

It will be observed that by putting both the tilting planes and theauxiliary propelling mechanism on the same oscillatable framework thereis obtained the double lifting effect of the rising or sustaining angle244. AERONAUTICS the machine has such climbing of the pivoted plane, ofthe upward pressure of the air striking the under side of the plane andthe pull upward at the same angle of the auxiliary propellers; and thisdouble synchronous lifting and sustaining power is in addition to theordinary power exerted by the upper and lower planes and gives to thismachine a far greater weight carrying or sustaining power than ispossessed with the old form of fixed rigid planes.

It will also be observed that constructing a machine in accordance withmy invention, and lifting power, and such flexibility of control thatits angle of flight can be quickly changed by the aviator from a levelto an upward one of forty degrees or more, and the pivoted plane is heldsecurely locked at the angle needed (by virtue of the worm and worm gearconnection 2728) until the height desired is attained, whereupon themidplanes and auxiliary propellers can be turned back to a levelparallel with the upper and lower planes and the machine thereuponbecomes an ordinary triplane in form but far more speedy and powerful.

Where speed alone is required, the additional force of the propellerswill greatly increase it, and, at the same time, will add to thestability of the aeroplane by positively keeping it on a level keel orline of flight and thus decrease the liability of accidents from suddengusts or changes of the wind which cause the side slip that is so oftenfatal.

It is also thought that by the use of the invention, the aeroplane willhave a far greater sustaining power in the light rarefied air of veryhigh altitudes of 20,000 feet or more, where the engine is much lessefiective on its present single propeller, for the auxiliary propellerswill greatly assist it in maintaining the Weight in the thin atmosphere.

The use of the invention will also enable the aeroplane to rise quicklyinto the air in starting, without the present need of a long run to gainmomentum, for, by tilting and locking the pivoted middle plane at asharp rising angle the air force will at once begin wedging it upwardand this force combined with theupward pull of the auxiliary propellersat the same angle will lift it clear almost instantly, thus enabling theaeroplane (or hydroplane, if such structure be present) to rise from thedeck length of a ship. Hydroplanes for coast guard or naval duty willthus be enabled to rise direct from the deck, or from the surface of thewater and in returning to the vessel, the aviator can tilt the middleplane to a lifting angle in descending and can graduate the speed byslowing down the engine until gravity overcomes propelling force and itwill settle down easily on the deck. This method of congrol alsoprevents landing accidents on lan The use of the invention-will greatlyincrease the practical values of aeroplanes for military use byincreasing the speed, by increasing its ability to carry weight oftorpedoes, bombs and machine guns and by the mere fact that it can bealmost poised in mid air while bombs are being actually dropped on theship, fort or other object to be destroyed; then the machine can easilysail away with all propellers driving forwardly.

By its increased speed and its power to climb rapidly into the air at amuch more acute angle than is now possible, an aeroplane equipped withthe present invention will be a most effective safe-guard againstZeppelins, for it will be quite impossible for them to escape from themachine guns and bombs of defending aviators using these machines. Ithas been thoroughly demonstrated during the present war that during allforms of aerial battle the aviator who can get his machine above hisopponent has the one below him at his mercy.

- Again, the invention will be especially suitable in naval use forscouting against submarines, for the middle plane can be set at alifting angle and all propellers slowed down until the lifting forcewill just overcome gravity at the slow speed which will enable theobserver to spot the submarine accurately. Having the ability to slowdown and almost poise in mid-air gives the aviator the power to drop,with deadly effeet, the under-water explosive bombs directly upon thesubmarine or, if the submarine is submerged, so near to it that it willbe destroyed; the dropping of bombs can be thus effected with greateraccuracy than is possible from a swiftly moving machine.

Full sized Fiske aerial torpedoes can also be easily carried and handledby a machine embodying the present invention and such machine willtherefore be more deadly and destructive in naval warfare than othermachines at present in use.

It will be observed that the present invention combines in a singlestructure three novel cooperative features namely: the distribution ofthe full power of the engines between a plurality of propellers in apractical manner to increase the propelling power; the use of a pivotedmidplane to increase the lifting and weight carrying ability; and thesynchronous movement of both the pivoted plane and the auxiliarypropellers through the arc of a circle to increase their lifting effectas desired.

From the foregoing description, taken in connection with theaccompanying drawings, it is thought the complete construction,

operation and advantages of the invention will be readily understood bythose skilled in the art.

WVhat I claim is:

1. An aeroplane having at least three sustaining planes extending tosubstantially equal planing distances at each side of the fuselage, twoof which are fixed and rigid, means for mounting an intermediate planeso that the same may be rotated on a transverse axis to change the angleof inclination, said aeroplane also having a main propelling mechanismincluding a power plant and a propeller, an auxiliary propellermechanism mounted on an axis to turn with the intermediate plane, andmeans under control of the aviator for tilting said intermediate planeand said auxiliary propeller mechanism to change the angle ofinclination at will.

2. An aeroplane having a fixed sustaining plane structure and a mainpropeller structure and power plant, combined with an auxiliarysustaining plane structure disposed parallel to the fixed sustainingplane structure, an auxiliary propeller structure disposed in a planeparallel to that containing the main propeller, and means for sustainingsaid auxiliary plane and said auxiliary propeller structure pivotally onan axis transversely of the aeroplane, and means for inclining saidauxiliary plane and said auxiliary propeller structure on the pivotalaxis.

3. An aeroplane having a fixed sustaining plane structure and a mainpropeller structure and power plant, combined with an auxiliarysustaining plane structure disposed parallel to the fixed sustainingplane structure, an auxiliary propeller structure disposed in a planeparallel to that containing the main propeller, and means for sustainingsaid auxiliary plane and said auxiliary propeller structure pivotally onan axis transversely of the aeroplane, and means for simultaneouslyinclining said auxiliary plane and said auxiliary propeller structure011 the pivotal axis whereby the same may move as a unit.

at. In an aeroplane having fixed upper and lower planes, a mainpropeller and power mechanism; an intermediate oscillatable plane, anauxiliary propelling mechanism fixed with relation to the intermediate,plane and bodily oscillatable therewith, means for mounting saidintermediate plane and said auxiliary propelling mechanism so that theywill be susceptible of inclination, and means for effecting theinclination of said intermediate plane and auxiliary propeller and meansfor driving said auxiliary propeller mechanism.

5. In an aeroplane having fixed upper and lower planes, a main propellerand power mechanism; an intermediate oscillatable plane, an auxiliarypropelling mechanism fixed with relation to the intermediate plane andbodily oscillatable therewith, means for mounting said intermediateplane and said auxiliary propelling mechanism so that they will besusceptible of inclination, means for effecting the inclination of saidintermediate plane and auxiliary propeller mechanism and means fordriving said auxiliary propeller mechanism from said main powermechanism.

6. In an aeroplane having fixed upper and lower planes, a main propellerand power mechanism; an intermediate oscillatable plane, an auxiliarypropelling mechanism fixed with relation to the intermediate plane andbodily oscillatable therewith, means for mounting said intermediateplane and said auxiliary propelling mechanism so that they will besusceptible of inclination, means for effecting the inclination of saidintermediate plane and auxiliary propeller mechanism as a unit about acommon axis, and means for driving said auxiliary propeller mechanism.

7. In an aeroplane having fixed upper and lower planes, a main propellerand power mechanism; an intermediate oscillatable plane, an auxiliarypropelling mechanism fixed with relation to the intermediate plane andbodily movable therewith, means for mounting said intermediate plane andsaid auxiliary propelling mechanism so that they will be susceptible ofinclination, means for effecting the inclination of said intermediateplane and auxiliary propelling mechanism, said means includingprovisions for locking the same to hold the intermediate plane and theauxiliary propelling mechanism in their various adjusted positions.

8. In an aeroplane having upper and lower sustaining planes, a mainpower plant engine located between said planes and a main propellerdriven by said engine; the combination of an auxiliary propellingmechanism and an intermediate sustaining plane journaled on a horizontalaxis between the upper and lower planes, said auxiliary propellingmechanism including an auxiliary propeller, a driving shaft and gearconnection between said auxiliary propeller and the power plant engineand including an auxiliary propeller shaft geared with the engine shaftand extending to project beyond the front of the planes on which shaftthe auxiliary propeller is located, and means for connecting saidintermediate plane with said auxiliary propeller mechanism, and meanswhereby said auxiliary propeller shaft and said intermediate plane maybe oscillated about a horizontal axis to change the inclination of thesame.

9. In an aeroplane having upper and lower sustaining planes, a mainpower plant engine located between said planes and a main propellerdriven by said engine; the

244, AtHUNAUHUS combination of an auxiliary propelling mechanism and anintermediate sustaining plane j ournaled on a horizontal axis betweenthe upper and lower planes, said auxiliary propelling mechanismincluding an auxiliary propeller, a driving shaft and gear connectionbetween said auxiliary propeller and the power plant engine andincluding an auxiliary propeller shaft geared with the engine shaft andextending to project beyond the front of the planes on which shaft theauxiliary propeller is located, means for connecting said intermediateplane with said auxiliary propeller mechanism, means whereby saidauxiliary propeller shaft and said intermediate plane may be oscillatedabout a horizontal axis to change the inclination of the same and meansfor locking said last named parts in their different adjusted positions.

10. In an aeroplane having upper and lower sustaining planes, a mainpower plant engine located between said planes and a main propellerdriven by said engine; the combination of an auxiliary propellingmechanism and an intermediate sustaining plane journaled on a horizontalaxis be tween the upper and lower planes, said auxiliary propellingmechanism including an auxiliary propeller, a driving shaft and gearconnection between said auxiliary propeller and the power plant engineand including an auxiliary propeller shaft geared with the engine shaftand extending to project beyond the front of the planes on which shaftthe auxiliary propeller is located, means for connecting saidintermediate plane with said auxiliary propeller mechanism, meanswhereby said auxiliary propeller shaft and said intermediate plane maybe oscillated about a horizontal axis to change the inclination of thesame, means for locking said last named parts in their differentadjusted positions, said last named means comprising an arcuate rack, anauxiliary propeller shaft housing to which said rack is secured, apinion meshing with said rack, a shaft connected with said pinion, andmeans under control of the aviator for turning said shaft.

11. In an aeroplane having upper and lower sustaining planes, a mainpower plant engine located between said planes and a main propellerdriven by said engine; the combination of an auxiliary propellingmechanism and an intermediate sustaining plane journaled on a horizontalaxis between the upper and lower planes, said auxiliary propellingmechanism including an auxiliary propeller, a driving shaft and gearconnection between said auxiliarv propeller and the power plant engineand including an auxiliary propeller shaft geared with the engine shaftand extending to proj ect beyond the front of the planes on which shaftthe auxiliary propeller is located, means for connecting saidintermediate plane with said auxiliary propeller mechanism, meanswhereby said auxiliary propeller shaft and said intermediate plane maybe oscillated about a horizontal axis to change the inclination of thesame, means for locking said last named parts in their differentadjusted positions, said last named means comprising an arcuate rack, anauxiliary propeller shaft housing to which said rack is secured, apinion meshing with said rack, a shaft connected with said pinion, meansunder control of the aviator for turning said shaft, said last namedmeans comprising a controlling shaft having a worm and worm gearconnection with said pinion shaft.

12. In an aeroplane having upper and lower sustaining planes, a mainpower plant engine located between said planes, a main propeller drivenby said engine; the combination of an auxiliary propelling mechanism andan intermediate plane journaled on a horizontal axis between the upperand lower planes, said auxiliary propelling mechanism including adriving shaft and gear connections with the power plant engine and alsoincluding an auxiliary propeller shaft geared with the driven shaft andextending to project beyond the front of the planes, an auxiliarypropeller carried by the projecting end of said auxiliary propellershaft, an arcuate rack connected with said auxiliary propeller mechanismand said intermediate plane for turning the same about the horizontalaxis to change the inclination of the same.

18. In an aeroplane structure which includes upper and lower mainsustaining planes, a fuselage, steering rudders, a plurality of mainpower engines, main propellers driven from said engines, the combinationof auxiliary propeller mechanism including an auxiliary propeller shaft,bearings in which said shaft is rotatable, means for mounting saidbearings to turn about a horizontal axis, drive gear connections betweenthe several main power plant engines, power transmission connectionsbetween the said engines and "the auxiliary propeller mechanism and alsomounted to turn on the horizontal axis with said auxiliary propellermechanism, and aviator controlled means for effecting the turning actionof said auxiliary propeller mechanism and said intermediate planes aboutthe horizontal axis.

14. In combination with an aeroplane having the usual upper and lowersustaining planes, fuselage, steering rudders, main power plant and mainpropeller units; an auxiliary propeller mechanism at each side of themachine, said auxiliary propeller mechanisms each including an auxiliarypropeller shaft, an auxiliary propeller and a housing for said auxiliarypropeller shaft, and means for mounting said housings to turn about atransverse horizontal axls, auxiliary sustaining planes at each side ofthemachine connected with the auxiliary propelling mechanism housingsand oscillatable about the horizontal axis therewith, a rack and piniondevice for effecting said oscillation, and aviator controlled means forindependently oscillating the auxiliary propelling mechanisms and theirrespective intermediate planes and means for driving said auxiliarypropellers from the main power plant.

15. In combination with an aeroplane having the usual upper and lowersustaining planes, fuselage, steering rudders, main power plant and mainpropeller units; an auxiliary propeller mechanism at each side of themachine, said auxiliary propeller mechanisms each including an auxiliarypropeller shaft, an auxiliary propeller, and a housing for saidauxiliary propeller shaft, means for mounting said housings to turnabout a transverse horizontal axis, auxiliary sustaining planes at eachside of the machine connected with the auxiliary propelling mechanismhousings and oscillatable about the horizontal axis therewith, a rackand pinion device for effecting said oscillation and aviator controlledmeans for independently and collectively oscillating the auxiliarypropelling mechanisms and their respective intermediate planes and meansfor driving said auxiliary propellers from the main power plant.

16. In combination with an aeroplane having the usual upper and lowersustaining planes, fuselage, steering rudders, main power plant and mainpropeller units; an auxiliary propeller mechanism at each side of themachine, said auxiliary propeller mechanisms each including an auxiliarypropeller shaft, an auxiliary propeller and a housing for said auxiliarypropeller shaft, means for mounting said housings to turn about atransverse horizontal axis, auxiliary sustaining planes at each side ofthe machine connected with the auxiliary propelling mechanism housingsand oscillatable about the horizontal axis therewith, a rack and piniondevice for effecting said oscillation, aviator controlled means forindependently oscillating the auxiliary propelling mechanisms and theirrespective intermediate planes, means for driving said auxiliarypropellers from the main power plant, said controlling means comprisingcontrolling shafts in reach of the aviator and irreversible gear andpower transmitting connections between said controlling shaft and thesaid auxiliary propeller mechanism and intermediate planes whereby thesame may be tilted by the aviator and locked in any position.

17. In combination with an aeroplane having the usual upper and lowersustaining planes, fuselage, steering rudders, main power plant and mainpropeller units; an auxiliary propeller mechanism at each side of themachine, said auxiliary propeller mechanisms each including an auxiliarypropeller shaft, an auxiliary propeller and a housing for said auxiliarypropeller shaft, means for mounting said housings to turn about atransverse horizontal axis, auxiliary sustaining planes at each side ofthe machine connected with the auxiliary propelling mechanism housingsand oscillatable about the horizontal axis therewith, a rack and piniondevice for effecting said oscillation, aviator controlled means forindependently and collectively oscillating the auxiliary propellingmechanisms and their respective intermediate planes, means for drivingsaid auxiliary propellers from the main power plant, said controllingmeans comprising controlling shafts in reach of the aviator andirreversible gear and power transmittin connections between saidcontrolling sha' and the said auxiliary propeller mechanism andintermediate planes whereby the same may be tilted by the aviator andlocked in any position.

JEAN F. WEBB, SR.

Copies of this patent may be obtained for five cents each, by addressingthe Commissioner of Iatents, Washington, D. G.

